Расчетно-теоретическое исследование взаимодействия высокотемпературного сверхзвукового потока с моделью летательного аппарата

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Расчетно-теоретическое исследование взаимодействия…
Инженерный журнал: наука и инновации # 12016 11
Numerical and theoretical research of high-temperature
supersonic flow interaction with the model
of flight vehicle profile
© D.A. Yagodnikov1, N.I. Bykov2, V.I. Tomak 1,
A.S. Burkov1 , Iryanov1
1Bauman Moscow State Technical University, Moscow, 105005, Russia
2S.P. Korolev Rocket and Space Corporation “Energia”, Korolev, 141070, Russia
The article considers the results of numerical and theoretical research of a high-
temperature flow with the specified velocity value (M = 4) around the flight vehicle ele-
ment profile model when total temperature of a free-stream flow is T* = 1134 K. The
free-stream flow consists of kerosene-air mixture combustion products flowing out from a
supersonic nozzle of the liquid rocket engine working to the liquid-gas scheme. This
scheme of model tests has advantages due to simplicity of realization, longer operation
time in comparison with impulse devices, and also allows to regulate total temperature of
the flow. The fields of working medium parameter distribution over the nozzle were ob-
tained by the finite element analysis using general-purpose program system ANSYS 14.5
when a gas generator worked at the optimal distance from the test object and without the
latter as well as in the presence of profile support which allowed determining the pres-
sure distribution over the surface of the test object and calculating the final force on the
supporting bracket. The minimum value of pressure in the working medium generator
chamber ensuring steady flow in the nozzle was also determined.
Keywords: profile supersonic flow, liquid rocket engine, numerical modeling, ANSYS.
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